CN102991666A - Laminated plate aircraft skin with flow control and deicing prevention functions - Google Patents
Laminated plate aircraft skin with flow control and deicing prevention functions Download PDFInfo
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- CN102991666A CN102991666A CN2012104853625A CN201210485362A CN102991666A CN 102991666 A CN102991666 A CN 102991666A CN 2012104853625 A CN2012104853625 A CN 2012104853625A CN 201210485362 A CN201210485362 A CN 201210485362A CN 102991666 A CN102991666 A CN 102991666A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B15/00—Layered products comprising a layer of metal
- B32B15/20—Layered products comprising a layer of metal comprising aluminium or copper
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B17/00—Layered products essentially comprising sheet glass, or glass, slag, or like fibres
- B32B17/06—Layered products essentially comprising sheet glass, or glass, slag, or like fibres comprising glass as the main or only constituent of a layer, next to another layer of a specific material
- B32B17/061—Layered products essentially comprising sheet glass, or glass, slag, or like fibres comprising glass as the main or only constituent of a layer, next to another layer of a specific material of metal
Abstract
The invention discloses a laminated plate aircraft skin with lift augmentation, resistance reduction, flow control and deicing prevention functions. The laminated plate aircraft skin comprises a glass fiber layer (2) and an aluminum alloy (1), wherein the glass fiber layer (2) and the aluminum alloy (1) are alternative; the surface of the skin is provided with an insulating material layer (4) and an electrode layer; the electrode layer is divided into an upper layer and a lower layer; the upper layer and the lower layer are respectively positioned on two sides of the insulating material layer (4) and are asymmetrically distributed; the upper electrode layer (3) is exposed in air and is connected with an alternating current power supply; and the lower electrode layer (5) is positioned below the insulating material layer (4) and is grounded. The laminated plate aircraft skin can be directly applied to aircraft manufacturing engineering, cannot be damaged by high-speed airflow and cannot bring parasite drag due to the damage of the original pneumatic shape. The deicing prevention function is realized by utilizing plasma heating on air and the pulse expansion wave function, the flow separation can be effectively controlled, the stall is delayed, the highest lift coefficient is increased, and the pressure difference resistance is reduced.
Description
Technical field
The present invention relates to a kind of composite panel aircraft skin that possesses the mobile controls such as lift-rising, drag reduction and anti-deicing function, belong to aircraft pneumatic design and structure design field.
Background technology
Fiber Reinforced Metal Laminates (Glare) covering (being designated hereinafter simply as composite panel) that alternately is formed by stacking by glass fibre and metal, be applied to Air Passenger A380, shown in Figure of description 1, it is compared at aspects such as tensile strength, crack expansion characteristic, losss of weight with the traditional metal covering has clear superiority.But this covering does not improve aircraft aerodynamic performance, the outer function of anti-deicing single-candidate.
At aircraft surfaces Plasma Actuator is installed, shown in Figure of description 2, can be suppressed flow separation, postpone stall, thereby reach the lift-rising drag reduction, improve the purpose of aircraft aerodynamic performance.If the employing nanosecond pulse power supply then can control effectively to separated flow under the flowing velocity that approaches practicality.In addition, can add hot air and apply the pulse expansion wave during Plasma Actuator work, therefore application potential is also arranged aspect anti-icing and deicing.But how Plasma Actuator properly being installed in aircraft surfaces is a technical barrier, and simple stickup not only is difficult to bear swiftly flowing impact, also can bring parasitic drag because destroying former pneumatic profile.
The Chinese patent of application number 200910080994.1 discloses a kind of plasma gurney flap, at the wing trailing edge Plasma Actuator is installed, and replaces traditional mechanical type gurney flap, carries out lift-rising control; The Chinese patent of application number 201010602315.5 discloses a kind of method of carrying out laminar flow control, separating control with Plasma Actuator; The Chinese patent of application number 201010253098.3 discloses a kind of apparatus and method of carrying out the control of wing tip whirlpool with Plasma Actuator.By which kind of mode Plasma Actuator is installed on aircraft surfaces but the foregoing invention patent is all undeclared, uses in addition very large distance from engineering.
Summary of the invention
The objective of the invention is: for composite panel aircraft skin function singleness, Plasma Actuator is difficult to firmly be installed on the problem of aircraft surfaces, the invention provides a kind of composite panel aircraft skin that possesses the several functions such as lift-rising drag reduction, anti-deicing.Metal electrode and the dielectric layer of Plasma Actuator are combined in the composite panel stressed-skin construction, thereby have overcome the deficiency of existing plasma flow control technology aspect installation, fully satisfy under the aircraft flight operating mode installation requirement to exiter.Make simultaneously this kind stressed-skin construction possess the control of flowing and anti-deicing function.
The technical scheme that the present invention takes is: a kind of composite panel aircraft skin that possesses flow control and anti-deicing function, comprise glass layer (2) and aluminium alloy layer (1), and glass layer (2) and aluminium alloy layer (1) are mutually alternately; Skin-surface is provided with insulation material layer (4) and electrode layer, electrode is divided into upper and lower two-layer, the two lays respectively at insulation material layer (4) both sides, be distribution or asymmetrical distribution, upper electrode layer (3) is exposed in the air, connect source of AC, lower electrode layer (5) is positioned under the insulation material layer (4), ground connection.
Described electrode layer (3,5) material is copper or aluminum alloy, and thickness is between 1/10mm～1/100mm.
Horizontal throw-2mm＜L＜2mm between described upper and lower electrode (3,5), the two has overlapping L less than 0 expression.
Described insulation material layer (4) is polyimide (Kapton), polytetrafluoroethylene fibre plate (Teflon) or epoxy resin fiber plate.
Power supply (6) voltage that is used for to upper/lower electrode (3,5) power supply is 5000～10000 volts, and the power supply signal waveform can be microsecond sinusoidal waveform, microsecond square wave, microsecond chopping sea, microsecond sawtooth wave, also can be nanosecond pulse.
Compare with the plasma flow control technology in the existing laboratory, the present invention can directly apply to the aircraft manufacturing engineering, can not damaged by high velocity air, also can not bring parasitic drag because destroying original aerodynamic configuration.The present invention effectively flow separation controls, and postpones stall, increases maximum lift coefficient, reduces pressure drag.The calorific effect that produces when the present invention also can use work in addition and pulse expansion wave-wave shock-effect are prevented deicing, and this is applied as original application the of the present invention.
This achievement combines electrode-electric dielectric layer-electrode structure and the laminated structure of Plasma Actuator together in a creative way, with the two Integral design, one machine-shaping, solve Plasma Actuator and installed and fixed problem, invented the type aircraft covering that possesses simultaneously mobile control function and anti-deicing function.
Description of drawings
The typical conventional fibre plymetal of Fig. 1 stressed-skin construction scheme drawing, 1: aluminium alloy layer, 2: glass layer;
Fig. 2 Plasma Actuator scheme drawing, 3: top electrode, 4: insulating barrier, 5: bottom electrode, 6: power supply;
Fig. 3 comprises the novel stressed-skin construction scheme drawing of Plasma Actuator;
Fig. 4 microsecond discharge plasma exiter principle of work scheme drawing;
Fig. 5 nanosecond pulse discharge plasma exiter principle of work scheme drawing.
The specific embodiment
Below in conjunction with accompanying drawing manufacturing of the present invention and application are described in further detail, but not as the foundation of the present invention being done any restriction.
A kind of composite panel aircraft skin that possesses flow control and anti-deicing function comprises glass layer (2) and aluminium alloy layer (1), and glass layer (2) and aluminium alloy layer (1) are mutually alternately; Skin-surface is provided with insulation material layer (4) and electrode layer, electrode is divided into upper and lower two-layer, the two lays respectively at insulation material layer (4) both sides, be distribution or asymmetrical distribution, upper electrode layer (3) is exposed in the air, connect source of AC, lower electrode layer (5) is positioned under the insulation material layer (4), ground connection.
Described electrode layer (3,5) material is copper sheet or aluminum alloy sheet, and thickness is between 1/10mm～1/100mm.
Horizontal throw-2mm＜L＜2mm between described upper and lower electrode (3,5), the two has overlapping L less than null representation.
Described insulation material layer (4) is polyimide (Kapton), polytetrafluoroethylene fibre plate (Teflon) or epoxy resin fiber plate.
Manufacturing of the present invention and installation: at first, carry out surface treatment to the aluminium alloy layer in the covering, increase its adhesive property; According to preformed aircraft skin shape Design and manufacture forming mould; Will be through aluminium alloy plate, glass layer, insulation material layer and the electrode layer of list processing in order, as shown in Figure 3, laying is in forming mould, and is then once compressing in the high temperature and high pressure environment in autoclave.Stressed-skin construction after the moulding is carried out non-destructive test by the method for C scanning, check adhesive effect between each layer, to guarantee the Forming Quality of stressed-skin construction.The present invention is installed on aircraft wing, high lift device and other key positions surface as aircraft skin, can carries out the control of lift-rising drag reduction; The present invention is installed on the positions such as the leading edge of a wing, empennage leading edge, driving engine lip, can be used for anti-deicing.
Principle of work of the present invention: the exiter surface electrode is connect high pressure (such as the 5000-10000 volt), high-frequency alternating current (such as delicate interchange or nanosecond pulse), bottom electrode ground connection.When adopting microsecond ripple power supply, air is ionized near the exiter, produces the plasma under the barometric pressure.Charged particle causes the ion wind tangent with object plane under the effect of AC field, as shown in Figure 4.The acquisition of flowing in the boundary-layer flows to momentum and inputs rear the acceleration, and the ability reinforcement of opposing adverse pressure gradient, but establishment flow separation, and then postponement stall generation increase maximum lift coefficient, reduce the pressure drag of being brought by flow separation.Microsecond discharge plasma exiter can effectively be controlled less than the separation phenomenon in the flow field of 30 meter per seconds the incoming flow flow velocity.
Power supply (6) voltage that is used for to upper/lower electrode (3,5) power supply is 5000～10000 volts, and the power supply signal waveform can be microsecond sinusoidal waveform, microsecond square wave, microsecond chopping sea, microsecond sawtooth wave, also can be nanosecond pulse.
When adopting nanosecond pulse power supply, produce the TRANSIENT HIGH TEMPERATURE high pressure near the exiter, then produce the expansion shock wave, as shown in Figure 5, then can induce revolving whirlpool.Under these arousal effects, the separation phenomenon in the flow field can be inhibited, effectively the incoming flow of control stream scooter 50 meter per seconds or higher.
In the lift-rising drag reduction, the nanosecond pulse excitation can make more than near the air themperature rising 100K of top electrode, and it is more effective anti-icing directly to heat air ratio heater wing surface.Utilize the periodic vibration effect of shock wave, can play the effect of auxiliary deicing.
Claims (9)
1. a composite panel aircraft skin that possesses flow control and anti-deicing function comprises glass layer (2) and aluminium alloy layer (1), and glass layer (2) and aluminium alloy layer (1) are mutually alternately; It is characterized in that: skin-surface is provided with insulation material layer (4) and electrode layer, electrode is divided into upper and lower two-layer, the two lays respectively at insulation material layer (4) both sides, be distribution or asymmetrical distribution, upper electrode layer (3) is exposed in the air, connect source of AC, lower electrode layer (5) is positioned under the insulation material layer (4), ground connection.
2. the composite panel aircraft skin that possesses flow control and anti-deicing function according to claim 1, it is characterized in that: electrode layer (3,5) material is copper or aluminum alloy, and thickness is between 1/10mm～1/100mm.
3. the composite panel aircraft skin that possesses flow control and anti-deicing function according to claim 1 and 2, it is characterized in that: horizontal throw-2mm＜L＜2mm between upper and lower electrode (3,5), the two has overlapping L less than 0 expression.
4. the composite panel aircraft skin that possesses flow control and anti-deicing function according to claim 1, it is characterized in that: insulation material layer (4) is polyimide (Kapton), polytetrafluoroethylene fibre plate (Teflon) or epoxy resin fiber plate.
5. power supply (a 6) voltage that possesses composite panel aircraft skin upper/lower electrode (3, the 5) power supply of flow control and anti-deicing function according to claim 1 is 5000～10000 volts.
6. power supply according to claim 5 (6) is characterised in that: signal waveform can be microsecond sinusoidal waveform, microsecond square wave, microsecond chopping sea, microsecond sawtooth wave or nanosecond pulse.
7. make the method that possesses the composite panel aircraft skin of flow control and anti-deicing function according to claim 1 for one kind, it is characterized in that: the laying technology that adopts composite material, with the different layers of this Novel stack laminate aircraft skin structure in order laying on mould, then once compressing in the high temperature and high pressure environment in autoclave.
8. the composite panel aircraft skin that possesses flow control and anti-deicing function according to claim 1 is characterized in that: other positions that are installed on aircraft wing or high lift device or aircraft surfaces.
9. the composite panel aircraft skin that possesses flow control and anti-deicing function according to claim 1 is characterized in that: be installed on the leading edge of a wing or empennage leading edge or driving engine lip.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN2012104853625A CN102991666A (en) | 2012-11-26 | 2012-11-26 | Laminated plate aircraft skin with flow control and deicing prevention functions |
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| CN2012104853625A CN102991666A (en) | 2012-11-26 | 2012-11-26 | Laminated plate aircraft skin with flow control and deicing prevention functions |
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| CN2012104853625A Pending CN102991666A (en) | 2012-11-26 | 2012-11-26 | Laminated plate aircraft skin with flow control and deicing prevention functions |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103625639A (en) * | 2013-09-25 | 2014-03-12 | 中国商用飞机有限责任公司 | Method for controlling noises of leading edge slat of airplane |
| GB2517465A (en) * | 2013-08-21 | 2015-02-25 | Airbus Operations Ltd | Panel for an aircraft |
| CN104875894A (en) * | 2015-05-27 | 2015-09-02 | 西北工业大学 | Dielectric barrier discharge plasma anti-icing device and method |
| CN104890881A (en) * | 2015-05-27 | 2015-09-09 | 西北工业大学 | Icing removing device and method of dielectric barrier discharge plasma |
| CN106081054A (en) * | 2016-06-13 | 2016-11-09 | 中国人民解放军国防科学技术大学 | Microwave heating anti-deicing aircraft Meta Materials eyelid covering and preparation method thereof |
| CN106314800A (en) * | 2016-09-23 | 2017-01-11 | 中国人民解放军国防科学技术大学 | Ice breaking and removing method based on plasma impact jet flow |
| CN106494606A (en) * | 2015-09-06 | 2017-03-15 | 沈观清 | Hollow long endurance unmanned aircraft stressed-skin construction |
| CN107889335A (en) * | 2017-10-30 | 2018-04-06 | 西安交通大学 | High frequency nanosecond pulse dielectric barrier discharge anti-icing equipment and method |
| CN107914865A (en) * | 2017-11-27 | 2018-04-17 | 西北工业大学 | The virtual dynamic bionic apparatus and method of plasma for the leading edge of a wing |
| CN109436285A (en) * | 2018-10-30 | 2019-03-08 | 南京航空航天大学 | Integral hollow interlayer composite material visits ice function covering |
| CN112607032A (en) * | 2020-12-29 | 2021-04-06 | 重庆交通大学绿色航空技术研究院 | Device and method for realizing flow control and ice shape sensing control of aircraft |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2424784A1 (en) * | 1974-05-22 | 1975-12-04 | Eichenauer Fa Fritz | System preventing ice formation on aircraft parts - has resistance heater in shell covering the part |
| JPH02100347A (en) * | 1988-10-07 | 1990-04-12 | Mitsubishi Metal Corp | Substrate for semiconductor device |
| CN101422973A (en) * | 2008-12-10 | 2009-05-06 | 哈尔滨工业大学 | Mixed composite material laminate with bistable structure |
| CN101508338A (en) * | 2009-03-31 | 2009-08-19 | 北京航空航天大学 | Plasma gurney flap |
| CN102114910A (en) * | 2010-12-14 | 2011-07-06 | 大连海事大学 | Plasma wing flow control method |
-
2012
- 2012-11-26 CN CN2012104853625A patent/CN102991666A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2424784A1 (en) * | 1974-05-22 | 1975-12-04 | Eichenauer Fa Fritz | System preventing ice formation on aircraft parts - has resistance heater in shell covering the part |
| JPH02100347A (en) * | 1988-10-07 | 1990-04-12 | Mitsubishi Metal Corp | Substrate for semiconductor device |
| CN101422973A (en) * | 2008-12-10 | 2009-05-06 | 哈尔滨工业大学 | Mixed composite material laminate with bistable structure |
| CN101508338A (en) * | 2009-03-31 | 2009-08-19 | 北京航空航天大学 | Plasma gurney flap |
| CN102114910A (en) * | 2010-12-14 | 2011-07-06 | 大连海事大学 | Plasma wing flow control method |
Non-Patent Citations (1)
| Title |
|---|
| 王永贵等: "纤维金属层板技术与大型飞机", 《第18届玻璃钢/复合材料学术年会论文集》 * |
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2517465A (en) * | 2013-08-21 | 2015-02-25 | Airbus Operations Ltd | Panel for an aircraft |
| CN103625639A (en) * | 2013-09-25 | 2014-03-12 | 中国商用飞机有限责任公司 | Method for controlling noises of leading edge slat of airplane |
| CN103625639B (en) * | 2013-09-25 | 2017-12-05 | 中国商用飞机有限责任公司 | Leading-edge slat noise control method |
| CN104875894A (en) * | 2015-05-27 | 2015-09-02 | 西北工业大学 | Dielectric barrier discharge plasma anti-icing device and method |
| CN104890881A (en) * | 2015-05-27 | 2015-09-09 | 西北工业大学 | Icing removing device and method of dielectric barrier discharge plasma |
| CN106494606A (en) * | 2015-09-06 | 2017-03-15 | 沈观清 | Hollow long endurance unmanned aircraft stressed-skin construction |
| CN106081054A (en) * | 2016-06-13 | 2016-11-09 | 中国人民解放军国防科学技术大学 | Microwave heating anti-deicing aircraft Meta Materials eyelid covering and preparation method thereof |
| CN106314800A (en) * | 2016-09-23 | 2017-01-11 | 中国人民解放军国防科学技术大学 | Ice breaking and removing method based on plasma impact jet flow |
| CN107889335A (en) * | 2017-10-30 | 2018-04-06 | 西安交通大学 | High frequency nanosecond pulse dielectric barrier discharge anti-icing equipment and method |
| CN107914865A (en) * | 2017-11-27 | 2018-04-17 | 西北工业大学 | The virtual dynamic bionic apparatus and method of plasma for the leading edge of a wing |
| CN107914865B (en) * | 2017-11-27 | 2020-09-25 | 西北工业大学 | Plasma virtual dynamic bionic device and method for wing leading edge |
| CN109436285A (en) * | 2018-10-30 | 2019-03-08 | 南京航空航天大学 | Integral hollow interlayer composite material visits ice function covering |
| CN109436285B (en) * | 2018-10-30 | 2021-07-27 | 南京航空航天大学 | Integral hollow interlayer composite material ice-detecting functional skin |
| CN112607032A (en) * | 2020-12-29 | 2021-04-06 | 重庆交通大学绿色航空技术研究院 | Device and method for realizing flow control and ice shape sensing control of aircraft |
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